Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-sc20606-il-1000000-n5 Airfoil,sc20606-il Reynolds number,1000000 Ncrit,5 Mach,0 Max Cl/Cd,65.6287 Max Cl/Cd alpha,3.75 Url,http://airfoiltools.com/polar/csv?polar=xf-sc20606-il-1000000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -10.000,-0.6636,0.08106,0.07945,-0.0137,1.0000,0.0046 -9.750,-0.6755,0.07418,0.07261,-0.0183,1.0000,0.0046 -9.500,-0.6959,0.06157,0.05997,-0.0336,1.0000,0.0045 -9.250,-0.7447,0.02779,0.02491,-0.0509,1.0000,0.0050 -9.000,-0.7219,0.02262,0.01918,-0.0533,1.0000,0.0052 -8.750,-0.6958,0.01992,0.01611,-0.0547,1.0000,0.0054 -8.500,-0.6688,0.01791,0.01380,-0.0557,1.0000,0.0056 -8.250,-0.6415,0.01643,0.01210,-0.0565,1.0000,0.0057 -8.000,-0.6146,0.01552,0.01104,-0.0569,1.0000,0.0059 -7.750,-0.5877,0.01477,0.01017,-0.0572,1.0000,0.0061 -7.500,-0.5602,0.01386,0.00909,-0.0576,1.0000,0.0062 -7.250,-0.5311,0.01256,0.00760,-0.0584,1.0000,0.0064 -7.000,-0.5004,0.01122,0.00606,-0.0597,1.0000,0.0070 -6.750,-0.4725,0.01070,0.00549,-0.0601,1.0000,0.0075 -6.500,-0.4448,0.01031,0.00505,-0.0603,1.0000,0.0079 -6.250,-0.4170,0.00993,0.00460,-0.0606,1.0000,0.0082 -6.000,-0.3890,0.00956,0.00419,-0.0609,1.0000,0.0086 -5.750,-0.3609,0.00923,0.00380,-0.0611,1.0000,0.0090 -5.500,-0.3328,0.00893,0.00346,-0.0614,1.0000,0.0093 -5.250,-0.3049,0.00867,0.00316,-0.0616,1.0000,0.0097 -5.000,-0.2770,0.00848,0.00293,-0.0618,0.9999,0.0102 -4.750,-0.2452,0.00819,0.00259,-0.0628,0.9995,0.0114 -4.500,-0.2135,0.00795,0.00236,-0.0638,0.9991,0.0150 -4.250,-0.1817,0.00773,0.00219,-0.0648,0.9985,0.0224 -4.000,-0.1497,0.00757,0.00205,-0.0659,0.9978,0.0302 -3.750,-0.1174,0.00741,0.00191,-0.0670,0.9971,0.0384 -3.500,-0.0852,0.00723,0.00180,-0.0681,0.9964,0.0532 -3.250,-0.0525,0.00691,0.00169,-0.0695,0.9959,0.1048 -3.000,-0.0186,0.00657,0.00159,-0.0712,0.9954,0.1715 -2.750,0.0175,0.00625,0.00147,-0.0733,0.9945,0.2368 -2.500,0.0535,0.00588,0.00134,-0.0754,0.9922,0.3149 -2.250,0.0932,0.00530,0.00121,-0.0785,0.9888,0.4505 -2.000,0.1355,0.00485,0.00112,-0.0820,0.9846,0.5641 -1.750,0.1690,0.00473,0.00107,-0.0833,0.9783,0.5894 -1.500,0.2046,0.00458,0.00101,-0.0850,0.9672,0.6158 -1.250,0.2422,0.00449,0.00093,-0.0870,0.9423,0.6310 -1.000,0.2691,0.00466,0.00091,-0.0864,0.8643,0.6451 -0.750,0.2868,0.00611,0.00109,-0.0842,0.5406,0.6580 -0.500,0.3124,0.00683,0.00123,-0.0841,0.3735,0.6725 -0.250,0.3397,0.00719,0.00135,-0.0841,0.2890,0.6867 0.000,0.3669,0.00756,0.00148,-0.0841,0.2093,0.6981 0.250,0.3942,0.00792,0.00162,-0.0841,0.1368,0.7078 0.500,0.4214,0.00834,0.00178,-0.0841,0.0652,0.7160 0.750,0.4492,0.00854,0.00191,-0.0841,0.0442,0.7242 1.000,0.4771,0.00870,0.00207,-0.0841,0.0342,0.7316 1.250,0.5049,0.00888,0.00223,-0.0841,0.0252,0.7390 1.500,0.5326,0.00908,0.00240,-0.0841,0.0174,0.7454 1.750,0.5604,0.00929,0.00261,-0.0840,0.0133,0.7523 2.000,0.5879,0.00957,0.00292,-0.0838,0.0105,0.7582 2.250,0.6154,0.00984,0.00326,-0.0837,0.0098,0.7642 2.500,0.6429,0.01007,0.00353,-0.0836,0.0094,0.7699 2.750,0.6702,0.01037,0.00388,-0.0834,0.0090,0.7761 3.000,0.6973,0.01070,0.00428,-0.0832,0.0087,0.7824 3.250,0.7242,0.01106,0.00471,-0.0830,0.0083,0.7885 3.500,0.7510,0.01145,0.00518,-0.0827,0.0080,0.7946 3.750,0.7777,0.01185,0.00565,-0.0824,0.0076,0.8001 4.000,0.8043,0.01227,0.00613,-0.0822,0.0073,0.8059 4.250,0.8306,0.01276,0.00669,-0.0818,0.0069,0.8114 4.500,0.8558,0.01360,0.00765,-0.0813,0.0064,0.8173 5.000,0.9044,0.01616,0.01065,-0.0797,0.0059,0.8302 5.250,0.9301,0.01685,0.01146,-0.0793,0.0058,0.8364 5.500,0.9553,0.01759,0.01235,-0.0788,0.0056,0.8417 5.750,0.9796,0.01870,0.01365,-0.0781,0.0054,0.8472 6.000,1.0029,0.02020,0.01540,-0.0773,0.0053,0.8525 6.250,1.0249,0.02202,0.01752,-0.0762,0.0051,0.8587 6.500,1.0452,0.02436,0.02021,-0.0750,0.0050,0.8645 6.750,1.0616,0.02780,0.02411,-0.0732,0.0047,0.8703 7.000,1.0268,0.05128,0.04904,-0.0655,0.0041,0.8750 7.250,1.0253,0.05951,0.05758,-0.0642,0.0039,0.8810 7.500,1.0232,0.06674,0.06505,-0.0640,0.0038,0.8880 7.750,1.0169,0.07416,0.07266,-0.0648,0.0037,0.8954 8.250,0.9857,0.08953,0.08828,-0.0703,0.0037,0.9189 8.500,0.9590,0.09841,0.09724,-0.0780,0.0038,0.9539